At the design conditions of a single-stage axial compressor, the blade angle at rotor exit is \(30^\circ\). The absolute velocities at rotor inlet and exit are 140 m/s and 240 m/s, respectively. The relative flow velocities at rotor inlet and exit are 240 m/s and 140 m/s, respectively. Find the blade speed \(U\) at the mean radius (round off to two decimal places).
